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GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il)
Reynolds number: 100,000
Max Cl/Cd: 33.64 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe324-il-100000.txt
Download as CSV file: xf-goe324-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 324 (HANSA-BRANDENBURG) AIRFOIL             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2257   0.11022   0.10555  -0.0207   0.8117   0.0716
  -8.750  -0.2230   0.10818   0.10349  -0.0235   0.8045   0.0737
  -8.500  -0.2294   0.10733   0.10265  -0.0311   0.7979   0.0748
  -8.250  -0.2291   0.10462   0.09997  -0.0361   0.7906   0.0753
  -8.000  -0.2060   0.09945   0.09473  -0.0295   0.7843   0.0766
  -7.750  -0.1920   0.09631   0.09160  -0.0296   0.7766   0.0782
  -7.500  -0.1828   0.09363   0.08889  -0.0306   0.7698   0.0800
  -7.250  -0.1754   0.09107   0.08632  -0.0325   0.7637   0.0821
  -7.000  -0.1698   0.08867   0.08395  -0.0372   0.7566   0.0846
  -6.750  -0.1621   0.08721   0.08224  -0.0550   0.7512   0.0870
  -6.500  -0.1502   0.08233   0.07749  -0.0494   0.7452   0.0880
  -6.250  -0.1362   0.07933   0.07453  -0.0472   0.7378   0.0897
  -6.000  -0.1234   0.07677   0.07192  -0.0474   0.7320   0.0922
  -5.750  -0.1067   0.07412   0.06923  -0.0510   0.7253   0.0963
  -5.500  -0.0853   0.07102   0.06589  -0.0608   0.7189   0.1015
  -5.250  -0.0734   0.06805   0.06298  -0.0579   0.7137   0.1037
  -5.000  -0.0556   0.06579   0.06073  -0.0586   0.7070   0.1080
  -4.750  -0.0285   0.06343   0.05801  -0.0661   0.7005   0.1167
  -4.500  -0.0150   0.06039   0.05503  -0.0641   0.6955   0.1191
  -4.250   0.0049   0.05833   0.05299  -0.0647   0.6884   0.1244
  -3.750   0.0481   0.05372   0.04812  -0.0675   0.6775   0.1390
  -3.500   0.0741   0.05192   0.04611  -0.0703   0.6712   0.1516
  -3.250   0.0946   0.05005   0.04428  -0.0702   0.6645   0.1596
  -3.000   0.1168   0.04798   0.04205  -0.0706   0.6599   0.1726
  -2.750   0.1395   0.04637   0.04035  -0.0713   0.6543   0.1895
  -2.500   0.1615   0.04494   0.03893  -0.0718   0.6473   0.2094
  -2.250   0.1825   0.04352   0.03742  -0.0716   0.6428   0.2430
  -2.000   0.2007   0.04199   0.03588  -0.0702   0.6393   0.2811
  -1.750   0.2181   0.04099   0.03508  -0.0697   0.6316   0.3210
  -1.500   0.2375   0.04006   0.03416  -0.0684   0.6263   0.3702
  -1.250   0.2534   0.03798   0.03218  -0.0656   0.6227   0.4149
  -1.000   0.2726   0.03676   0.03103  -0.0641   0.6181   0.4547
  -0.750   0.2978   0.03601   0.03031  -0.0651   0.6112   0.4763
  -0.500   0.4002   0.03578   0.02736  -0.0757   0.6067   0.1482
  -0.250   0.4304   0.03396   0.02526  -0.0749   0.6037   0.1280
   0.000   0.4575   0.03390   0.02497  -0.0753   0.5970   0.1181
   0.250   0.4843   0.03382   0.02477  -0.0753   0.5914   0.1129
   0.500   0.5126   0.03295   0.02375  -0.0746   0.5878   0.1082
   0.750   0.5421   0.03215   0.02268  -0.0735   0.5851   0.1040
   1.000   0.5635   0.03327   0.02386  -0.0743   0.5768   0.1024
   1.250   0.5895   0.03319   0.02375  -0.0739   0.5721   0.1019
   1.500   0.6173   0.03248   0.02305  -0.0730   0.5690   0.1044
   1.750   0.6456   0.03180   0.02233  -0.0719   0.5667   0.1088
   2.000   0.6602   0.03390   0.02464  -0.0730   0.5564   0.1110
   2.250   0.6877   0.03348   0.02413  -0.0719   0.5527   0.1147
   2.500   0.7185   0.03261   0.02314  -0.0708   0.5502   0.1227
   2.750   0.7322   0.03481   0.02548  -0.0716   0.5400   0.1336
   3.000   0.7651   0.03228   0.02490  -0.0711   0.5361   1.0000
   3.250   0.7971   0.03163   0.02382  -0.0698   0.5336   1.0000
   3.500   0.8075   0.03416   0.02639  -0.0701   0.5236   1.0000
   3.750   0.8353   0.03402   0.02607  -0.0693   0.5194   1.0000
   4.000   0.8679   0.03324   0.02509  -0.0683   0.5169   1.0000
   4.250   0.8739   0.03621   0.02817  -0.0686   0.5065   1.0000
   4.500   0.9028   0.03589   0.02774  -0.0678   0.5026   1.0000
   4.750   0.9371   0.03489   0.02659  -0.0669   0.5003   1.0000
   5.000   0.9721   0.03389   0.02543  -0.0660   0.4983   1.0000
   5.250   0.9706   0.03745   0.02919  -0.0660   0.4857   1.0000
   5.500   1.0077   0.03614   0.02775  -0.0652   0.4836   1.0000
   5.750   1.0441   0.03502   0.02650  -0.0645   0.4816   1.0000
   6.000   1.0383   0.03885   0.03055  -0.0642   0.4688   1.0000
   6.250   1.0781   0.03726   0.02884  -0.0635   0.4668   1.0000
   6.500   1.0682   0.04134   0.03310  -0.0629   0.4541   1.0000
   6.750   1.1098   0.03953   0.03121  -0.0621   0.4520   1.0000
   7.000   1.1512   0.03788   0.02945  -0.0616   0.4499   1.0000
   7.250   1.0388   0.05359   0.04555  -0.0620   0.4209   1.0000
   7.500   1.1210   0.04672   0.03861  -0.0599   0.4261   1.0000
   7.750   1.1981   0.04126   0.03300  -0.0594   0.4292   1.0000
   8.000   1.1972   0.04386   0.03570  -0.0583   0.4196   1.0000
   8.250   1.2490   0.04121   0.03297  -0.0581   0.4178   1.0000
   8.500   1.3018   0.03870   0.03030  -0.0582   0.4157   1.0000
   8.750   1.1957   0.05159   0.04359  -0.0556   0.3965   1.0000
   9.000   1.2686   0.04665   0.03861  -0.0549   0.3963   1.0000
   9.250   1.2179   0.05446   0.04652  -0.0542   0.3844   1.0000
   9.500   1.3053   0.04759   0.03963  -0.0531   0.3850   1.0000
   9.750   1.3911   0.04227   0.03416  -0.0542   0.3837   1.0000
  10.000   1.2485   0.05912   0.05129  -0.0523   0.3671   1.0000
  10.250   1.3419   0.05085   0.04302  -0.0504   0.3679   1.0000
  10.500   1.4533   0.04353   0.03553  -0.0521   0.3669   1.0000
  10.750   0.8711   0.12994   0.12246  -0.0745   0.3541   1.0000
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